Rotary explosion engine



Jan. 30, 1968 'r. E. MATHEWS ROTARY EXPLOSION ENGINE Filed March 11, 1966 INVENTOR. 77/0/ 445 6 MAW/1445 Lay/W504 A r rogue K5 United States atent ()fifice 3,366,096 ROTARY EXPLOSION ENGINE Thomas E. Mathews, 402 4th St. NE., Auburn, Wash. 98002 Filed Mar. 11, 1966, Ser. No. 533,537 6 Claims. (Cl. 123-13) ABSTRACT OF THE DISCLOSURE An engine including a rotary compressor having a bilobe rotary impeller and a complementary bi-recess rotary abutment. Axial discharge from a point in a radial stator wall portion of the compressor that is swept by both the lobes and the recesses, into one or the other of a pair of diametrically opposed explosion chambers formed in a power rotor portion of the engine.

The present invention relates to rotary positive displacement gas compressors, and to rotary explosion engines utilizing such compressors, and in addition comprising a single power rotor having a pair of diametrically opposed explosion chambers, and means for sequentially igniting explosive charges in said chambers, at the rate of one explosion per chamber, per revolution of the power rotor.

Rotary compressors according to the present invention are characterized essentially by a bilobe rotary impeller and a single bi-recess abutment, in use coacting to compress two air or fuel/air charges per revolution. The impeller is housed in a cylindrical compressor chamber, and the abutment is housed partially in a generally cylindrical abutment chamber located at the periphery of the compressor chamber and opening into it, and partially within the compressor chamber. The compressor housing includes a radial stator wall forming an end boundary of both the compressor and abutment chambers. A shaft extends axially through the compressor chamber, and the impeller is supported for rotation in the compressor chamber by such shaft. The impeller includes a cylindrical hub of a diameter substantially smaller than the diameter of said compressor chamber, and the two lobes project from diametrically opposed locations on said hub radially out-wardly to the inner cylindrical surface of the com pressor housing. The abutment is journaled for rotation in said abutment chamber, and also partially within the adjoining portion of the compressor chamber. The impeller and the rotary abutments are rotated in opposite directions, but at the same angular velocity. During rotation the cylindrical periphery of the abutment is in sealing engagement with the cylindrical periphery of the impeller hub, and each lobe enters into and rotates relatively through the abutment recess associated with it. Between the recesses the abutment presents closed end surfaces towards the stator end wall. The compressor outlet is located in the stator end wall at a position that is traversed by the end surfaces of the impeller lobes, and also by the end openings of the abutment recesses and the closed end surfaces of the abutment between the recesses.

Fischer 1,311,858 and Sunderland 2,070,631 both disclose a rotary compressor having a bi-lobe impeller, but such compressors also include two single recess abutments. Furthermore, in Fischer 1,311,858 the compressed gas outflow is first axially and then radially through the abutments, rather than axially through a radial stator wall common to both the compressor and abutment chambers. In Sunderland 2,070,631 the compressed gas outflow is radially through the impeller hub to a prime mover positioned radially inwardly of the compressor chamber.

Another object of the present invention is to provide a rotary explosion engine comprising a compressor of the 3,366,096 Patented Jan. 30, 1968 character described, and a prime mover including a cylindrical prime mover chamber axially aligned with the compressor chamber, with said shaft extending from said compressor chamber and axially through said prime mover chamber. A power rotor is supported for rotation in said prime mover chamber by the shaft. The power rotor includes a pair of diametrically opposed peripheral explosion chambers. The power rotor presents a closed surface to the outlet of said passageway between the explosion chambers. The passageway leading from the working space of the compressor enters the prime mover at a location in the rotational path of the explosion chambers. The prime mover also includes means for igniting a mixture of fuel and air in each explosion chamber relatively soon after it rotates passed communication with the compressed charge inlet, and a peripheral outlet leading generally tangentially from the prime mover chamber, at a location circumferentially forwardly of where ignition took place.

A further object of the present invention is to provide a rotary explosion engine of the character described, in which the radial stator wall extends between and forms a common end boundary for both the compressor and prime mover chambers, and the passageway communicating the two extends generally axially through said wall.

A still further object of the present invention is to pro vi-de a rotary explosion engine of the character described, and which comprises two prime movers, one on each side the compressor.

Yet another object of the present invention is to provide a rotary engine that combines the power and economy of reciprocating piston type engines with the balance and simplicity of a turbine engine, and which involves but a relatively few parts and is comparatively inexpensive to manufacture, but is capable of producing a relatively high degree of torque.

A still further object of the present invention is to provide a rotary explosion engine of the character described that includes end seals for the power rotor in the form of seal members inset into the stator end walls of the prime mover chamber, and extending diametrically across said walls, and adapted to exert a slight constant pressure on the end surfaces of the rotor.

These and other objects, features, and advantages of the present invention will be apparent from the following description, appended claims and annexed drawings.

Referring to the drawing wherein like reference characters designate like parts throughout the several views:

FIG. 1 is a view in longitudinal section, taken substantially along line 1-1 of FIGS. 2 and 6;

FIG. 2 is a view in cross-section of the mechanism shown in FIG. 1, taken substantially along line 2-2 of FIG. 1;

FIG. 3 is a fragmentary view taken from the same aspect as FIG. 2, but showing one of the lobes about to enter the abutment recess with which it is associated;

FIG. 4 is a view like FIG. 3, but showing the lobe halfway through its recess;

FIG. 5 is a view like FIGS. 3 and lobe about to leave its recess;

FIG. 6 is a view in cross-section taken through the mechanism substantially along line 66 of FIG. 1;

FIG. 7 is a view like FIG. 6, but with the rotor advanced somewhat from its FIG. 6 position;

FIG. 8 is a view like FIG. 6, but of a modified form of power rotor; and

FIG. 9 is a fragmentary detail view, on an enlarged scale, taken substantially along line 99 of FIG. 1, and showing the way in which the power rotor seal is insert into its stator wall.

Referring more specifically to the several figures of the drawing, the engine is shown to comprise a housing or 4, but showing the stator including a compressor section positioned between two prime mover sections 12, 12'. The compressor and prime mover chambers are axially aligned, are cylindrieal, and are all about equal in diameter. A generally cylindrical abutment chamber 14 is located generally at the periphery of, and opens into, the compressor chamber 10. A shaft 16 extends axially through all three chambers 10, 12, 12.

An impeller 18 having parallel generally planar end surfaces is supported for rotation in the compressor section 10 by the shaft 16. Impeller 18 includes a cylindrical hub 20 and a pair of diametrically opposed lobes 22 which project radially outwardly from said hub 20 and at their ends are in sealed engagement with the cylindrical inner surface of the compressor chamber. The cylindrical peripheral surface of the hub 20 and the cylindrical inner surface of the compressor housing together form an annular working space, and the lobes 22 divide such working space into two generally semiannular working chambers.

A cylindrical rotary abutment 24 is journaled, preferably by a shaft 26 and support bearings therefor (not shown), for rotation partially in the abutment chamber 14 and partially in the adjoining portion of the compressor working space. As illustrated (FIG. 2, for example), the impeller 18 and the abutment 24 rotate in opposite direction, and throughout the greatest part of each revolution the cylindrical peripheral surface of the abutment 24 engages and preferably makes fluid tight contact with the cylindrical peripheral surface of the impeller hub 20. The abutment 24 includes a pair of diametrically opposed peripheral recesses 28 which are positioned and configured for receiving and permitting passage of the impeller lobes 22. The abutment 24 is equal in width to the impeller 18, and its has blank end surfaces between the open ends of the recesses 23, which surfaces are coplanar with the end surfaces of the impeller 18.

The compressor section 10 is bounded at each end by a radial stator wall 30, 30, each of which extends contiguous an end surface of the impeller 18 and an end surface of the abutment 24. Preferably, the stator walls 30, 30' each also form an end boundary for the prime mover chamber 12, 12 at its end of the engine.

The abutment 24 is preferably driven from the main drive shaft 16. In FIG. 1, a drive gear 50 is shown secured to an end portion of the shaft 16 within the confines of an auxiliary housing 52. Gear 50 is in mesh with a similar gear 54 affixed to a parallel stub shaft 56 which is journaled generally radially outwardly from the main shaft 16. A sprocket or pulley 58 is secured to the stub shaft 56 adjacent the gear 54, and rotates in parallelism with a similar sprocket or pulley 60 aflixed to the abutment shaft 26. A drive chain or belt is looped over and interconnects the sprockets or pulleys 58, 60. The gears 50, 54, and the sprockets or pulleys 58, 60 are chosen to be of such a size that the angular velocity of abutment 24 is identical to the angular velocity of impeller 18. Of course, a train of gearing could be used in place of the chain and sprocket or belt and pulley drive means.

Referring now to FIGS. 3-5, in FIG. 3 the tip of an abutment 22 is shown to substantially meet the trailing arc end of a recess 28 at station 64. Upon thirty degrees (30) additional rotation of both the impeller 18 and the abutment 24 the radial center of such lobe 22 coincides with the radial center of such recess 28 (FIG. 4). Upon an additional thirty degrees (30") rotation of both the impeller 18 and the abutment 24, the tip of such abutment 22 meets the leading arc end of such recess 28 at station 65, substantially one hundred and twenty degrees (120) removed from station 64 from the axis of rotation of the abutment 24, and sixty degrees (60) about the axis of impeller 18. As the lobe 22 rotates relatively through the recess 28, it slides relatively along and is in sealing engagement with the concave inner surface of the recess 28.

A power rotor or reaction wheel 32, 32' is journaled for rotation in each prime mover chamber 12, 12' by the shaft 16. Each power rotor 32, 32 includes a diametrically opposed pair of peripheral combustion or reaction chambers 34, 34. An opening or passageway 36, 36 extends axially through each stator wall 30, 30 in the vicinity of the abutment 24 and serves to communicate the working chambers of the compressor with the combustion chambers 34, 34 of the prime movers. As best shown by FIG. 2, the passageways 36, 36 are positioned in an area of the stator wall 30, 30 that is traversed by the ends of both the abutment 24 and the lobes 22 during rotation of the abutment 24 and the impeller 18, respectively. The compressor inlet 38 is positioned adjacent and slightly forwardly of the abutment chamber 14. A carbureted mixture of fuel and air may be delivered into the inlet 38 from a carburetor 40, or air alone may be supplied to the inlet 38, with the fuel being injected directly into the combustion chamber 34, 34' by independent injector device.

An ignition station 40 is located forwardly of the passageways 36, 36' in the direction of rotation of the rotors 32, 32. A spark plug 42 or other suitable intermittent ignition device or ignitor may extend through a wall of the prime mover chamber at the ignitiOn station 40. The peripheral wall of the prime mover housing may bulge outwardly at the ignition station 40, as illustrated, and sized to form with an explosion chamber 34, 34 the desired explosion chamber volume to suit the energy level sought. A peripheral outlet 44 leads generally tangentially from the prime mover chamber, at a location circumferentially forwardly of the ignition station 40.

In preferred form, a diametrical groove 46 is formed in each stator end Wall of each prime mover chamber, and a metallic seal member 48 is snugly received in said groove. A series of generally flat leaf springs may be bottomed in the groove 46, rearwardly of the seal member 48. The leaf springs exert a push on the seal members 48, urging them toward the end surfaces of the rotors 32, 32, so that they exert a slight constant pressure on the end surfaces of the rotors 32, 32.

In operation: as each impeller lobe 22 rotates passed the compressor inlet 38 air enters through inlet 38 into the space behind the lobe 22. When the second lobe passes the inlet 38, substantially behind the first lobe, a charge of gas is trapped in the space or pocket between the lobes 22, and will be moved toward the abutment 24 as the impeller 18 continues to rotate. Once the leading lobe 22 passes the abutment 24, the space between the abutment 24 and the trailing lobe 22, in which such charge is trapped, begins to diminish in size. The compressor outlet port 36 is closed by the valving action of the closed end surface of the abutment 24 between the recesses 28. Thus, as the charge zone decreases in size the charge is compressed between the lobe 22 and the abutment 24. When the tip of lobe 22 is approximately forty-five degrees (45) away from the juncture of the compressor housing with the abutment housing (designated 64 in the drawing) the abutment 24 commences to uncover the compressor outlet port 36, and then during about the next approximately fifty degrees (50) of impeller rotation the charge is forced through the passageways 36, 36 into the pair of reaction chambers 34, 34 which are at that time in registry with the ports 36, 36' on the opposite side of the stator walls 30, 3t).

Initially, the engine of this invention may be put in motion by a starter, the shaft of which is shown in FIG. 1, and is designated 66. The starter shaft 66 is shown connected to the main shaft 16 by a clutch 68. When the engine is running under its own power the clutch 68 disengages, and the shaft 16 is turned by the power rotors 32, 32'. When a reaction chamber 34, 34' is at the ignition station 40, the ignitor 42 is energized. The explosion gases or combustion products are then exhausted generally tangentially out through the prime mover 44.

Although the explosion engine of the present invention has been illustrated and described as having two prime movers, it is to be understood that one of the prime movers could be eliminated. The ignitor may be carried by the rotor rather than the stator. Although it is preferred that a carbureted fuel-air mixture be delivered into and compressed by the compressor 10, air alone may be compressed, with the fuel being injected directly into the combustion chamber. The power rotor may take the form illustrated by FIG. 8, in which the reaction chambers RC possess the same general shape as the rocket reaction chambers, complete with venturi sections 65 and expansion nozzles 67. In FIG. 8 the spark plugs 69 are shown to be carried by the rotor.

Although the common axis of rotation of the compressor and prime movers is shown to be horizontally disposed, it is not limited to this disposition. Such axis (and the axis of the compressor when used apart from the prime movers) may be vertically disposed, or even between a horiozntal and a vertical disposition. The compressor also has utility as a pump for oil or other liquids.

Having thus described the invention, it is clear that the objects as stated have been obtained in a simple and practical manner.

The volume of each working chamber of the compressor or pump is large in comparison with each prime mover chamber, thus a large compression ratio is provided. Location of the prime mover chambers at the periphery of the prime mover rotor provides maximum leverage during the power phase. A balanced rotation is provided, i.e. no counterbalancing is required.

While certain practical embodiments of the invention have been shown and described, it is understood that further changes may be made in the construction and arrangement of the various parts without departing from the spirit and scope of the invention as expressed in the following claims.

What is claimed is:

1. A rotary explosion engine comprising a compressor including housing means forming a cylindrical compressor chamber, and a cylindrical abutment chamber generally at the periphery of, and opening radially inwardly into, the compressor chamber, said housing means including a radial stator wall forming an end boundary of both the compressor and abutment chambers, a shaft extending axially through said compressor chamber; an impeller in said compressor chamber supported for rotation by said shaft, and having a cylindrical hub of a diameter substantially smaller than the diameter of said compressor chamber, and a pair of diametrically opposed lobes projecting radially outwardly from said hub to the inner cylindrical surface of said compressor housing, with the cylindrical peripheral surface of said hub and the cylindrical inner surface of the compressor housing defining between them a generally annular working space that is bounded at one end by the stator wall and divided into two separate working chambers by said lobes; a cylindrical rotary abutment journaled for rotation in said abutment chamber, and also partially within the adjoining portion of said annular working space, with its periphery contiguous the periphery of said h-ub, said abutment including a pair of diametrically opposed peripheral recesses positioned and configured for receiving and permitting passage of the impeller lobes as said abutment and said impeller rotate in opposite directions and at the same angular velocity, said recesses opening axially towards said stator wall, and said abutment presenting a closed end surface towards the stator wall between said recesses; a peripheral inlet for said working space positioned adjacent the abutment; a passageway leading out from said working space, and including an inlet entering said stator wall at a position that is traversed by the end surfaces of the impeller lobes, and also by the end openings of the abutment recesses and the closed end surfaces of the abutment between the recesses, during rotation of the impeller and the abutment; and means for rotating the impeller and the abutment in opposite directions, and at the same angular velocity, with the direction of the impeller movement being the direction involving the greater distance from the working chamber inlet to the abutment; and a prime mover including a cylindrical prime mover chamber axially aligned with the compressor chamber, with said shaft extending from said compressor chamber and axially through said prime mover chamber; a power rotor in said prime mover chamber supported for rotation by said shaft, and including a pair of diametrically opposed peripheral explosion chambers, with the passageway which leads from the working space of the compressor leading into the prime mover at a location in the rotation path of the explosion chambers, and with the power rotor presenting a closed surface to the outlet of said passageway between the explosion chambers; means for igniting a mixture of fuel and air in each explosion chamber relatively soon after it rotates passed communication with the outlet of said passageway; and peripheral outlet leading generally tangentially from said prime mover chamber, at a location circumferentially forwarding of where ignition took place.

2. A rotary explosion engine according to claim 1, further including means for delivering a carbureted mixture of fuel and air to compressor inlet.

3. A rotary explosion engine according to claim 1, including a radial stator wall contiguous each end of the power rotor, and a seal member inset in each stator wall, extending diametrically across the wall, and exerting a slight constant pressure on the end surface of the rotor.

4. A rotary explosion engine according to claim 1, wherein said radial stator wall extends between and forms a common end boundary for both the compressor and prime mover chambers, and said passageway extends generally axially through said wall.

5. A rotary explosion engine according to claim 3, wherein in each recess the angle between radial lines leading outwardly from the rotational center of the abutment to the arc ends of the recess is substantially sixty degrees.

6. A rotary explosion engine according to claim 3, further including housing means forming a second prime mover chamber on the side of the compressor opposite the first prime mover, with said shaft also extending through said second prime mover chamber; a second radial stator wall between and forming a common end boundary for both the compressor and the second prime mover chambers, said wall including an axial passageway communicating the working space of the compressor with the combustion chambers of the prime mover, and generally coaxially related with the counterpart passageway in said first stator wall; a power rotor in said second prime mover chamber, supported for rotation by said shaft and having a pair of diametrically opposed explosion chambers which are identical to and are axially aligned with the explosion chambers of the power rotor in the first prime mover chamber; and an outlet generally corresponding in position to the outlet for the first prime mover.

References Cited UNITED STATES PATENTS 2,715,391 8/1955 Smith 123-13 2,956,735 10/1960 Breelle 230- RALPH D. BLAKESLEE, Primary Examiner. 

